CN110793624A - Sound source calibrating device used in high-speed airflow - Google Patents
Sound source calibrating device used in high-speed airflow Download PDFInfo
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- CN110793624A CN110793624A CN201911247482.XA CN201911247482A CN110793624A CN 110793624 A CN110793624 A CN 110793624A CN 201911247482 A CN201911247482 A CN 201911247482A CN 110793624 A CN110793624 A CN 110793624A
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- 230000005540 biological transmission Effects 0.000 claims abstract description 29
- 238000004519 manufacturing process Methods 0.000 claims abstract description 13
- 239000004744 fabric Substances 0.000 claims abstract description 5
- 238000012360 testing method Methods 0.000 abstract description 14
- 238000009434 installation Methods 0.000 description 4
- 238000007789 sealing Methods 0.000 description 3
- 238000012937 correction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the preceding groups
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- Soundproofing, Sound Blocking, And Sound Damping (AREA)
Abstract
The invention provides a sound source calibrating device used in high-speed airflow, which is used for calibrating a noise testing system during a pneumatic noise wind tunnel test and can improve the positioning precision and efficiency of a noise source. The device comprises a fairing assembly, a support frame, a loudspeaker, a sound transmission channel and a support rod, wherein the fairing assembly is provided with a sound transmission hole; the sound transmission holes are covered with a layer of Kaffra cloth. The device has the advantages of small sound production area and good directivity.
Description
Technical Field
The invention belongs to the technical field of noise measurement, and relates to a sound source calibrating device used in high-speed airflow.
Background
When a pneumatic noise test is performed in an acoustic wind tunnel, on one hand, a noise test system needs to be calibrated on site to ensure that the noise test system works normally under the action of high-speed airflow, and on the other hand, the high-speed airflow influences the propagation of sound waves, changes the propagation direction and strength of the sound waves and influences the noise test result, so that the influence of the high-speed airflow on the noise test result needs to be obtained, and corresponding correction and processing are performed. The conventional calibration sound source is generally a spherical or square sound source, has the defects of large volume, poor aerodynamic shape, large sound source area and the like, is subjected to large aerodynamic force when arranged in high-speed airflow, seriously disturbs a flow field, generates additional interference noise, and is difficult to meet the requirement of calibrating a noise test system in the high-speed airflow. The invention designs a calibration sound source which can be used in high-speed airflow, and the sound source has good pneumatic appearance and lower pneumatic load, and does not generate extra pneumatic noise; the high-sound-intensity loudspeaker is adopted for sound production, and the device has the advantages of wide frequency range, strong sound production capability, stable sound production effect, controllable sound production mode and the like; the sound waves radiate noise through the sound-transmitting holes, and the sound source has the advantages of small sound source area, good directivity and the like. The calibration sound source can be used for multiple purposes such as noise test system inspection calibration, airflow influence analysis and correction, microphone phase array performance evaluation under the condition of airflow and the like, and can improve the noise measurement accuracy in the acoustic wind tunnel.
Disclosure of Invention
Based on the defects, the invention provides the sound source calibrating device used in the high-speed airflow, which is used for calibrating the noise testing system during the pneumatic noise wind tunnel test and can improve the precision and efficiency of positioning the noise source.
The technology adopted by the invention is as follows: a sound source calibrating device used in high-speed airflow comprises a fairing assembly, a supporting frame, a loudspeaker, a sound transmission channel and a supporting rod, wherein the fairing assembly is provided with a sound transmission hole; the sound transmission holes are covered with a layer of Kaffra cloth.
The invention also has the following technical characteristics:
1. the fairing assembly comprises a front segment fairing, a middle segment fairing and a rear segment fairing, wherein the interiors of the front segment fairing, the middle segment fairing and the rear segment fairing are respectively and fixedly connected with the supporting frame.
2. The loudspeaker is arranged in the middle-section fairing, and the sound transmission hole is formed in the middle-section fairing.
3. The fairing assembly as described above is an elliptical shaped rotating body structure, with the cross section of the fairing assembly corresponding to the airfoil curve.
4. The other end of the support rod is of a taper sleeve structure.
5. The inside of the supporting rod is provided with a wiring channel.
The invention has the advantages and beneficial effects that: the method is used for calibrating the noise test system during pneumatic noise wind tunnel test, and improves the precision and efficiency of positioning the noise source. The arrangement in high-speed airflow is facilitated, meanwhile, the interference to a flow field is reduced, and the generation of additional noise interference is avoided; secondly, the high sound intensity electric loudspeaker is adopted for sound production, and the high sound intensity electric loudspeaker has the advantages of strong sound production capability, stable sound production effect and reliable sound production mode; meanwhile, the microphone has the advantages of small sound production area and good directivity.
Drawings
FIG. 1 is a block diagram of an apparatus for calibrating a sound source for use in a high velocity air stream in accordance with the present invention; wherein
1-fairing, 2-sound-transmitting hole, 3-loudspeaker, 4-supporting frame, 5-sound-transmitting channel and 6-supporting rod
Detailed Description
The invention is further illustrated by way of example in the accompanying drawings of the specification:
example 1
As shown in fig. 1, a sound source calibration device for use in high-speed airflow comprises a fairing assembly, a support frame, a loudspeaker, a sound transmission channel and a support rod, wherein the fairing assembly is provided with a sound transmission hole, the loudspeaker and the support frame are both arranged in the fairing assembly, the loudspeaker is fixedly connected with the support frame, a sound production part of the loudspeaker is connected with an inlet of the sound transmission channel, the sound transmission channel is fixedly connected with the support frame, an outlet of the sound transmission channel is communicated with the sound transmission hole on the fairing assembly, and one end of the support rod penetrates through the fairing assembly and is fixedly connected with the support frame; the sound transmission holes are covered with a layer of Kaffra cloth. The fairing assembly comprises a front fairing, a middle fairing and a rear fairing, and each segment is fixedly connected with the support frame through a screw. The middle section radome fairing is divided into two halves along the axial, the installation, the wiring and the maintenance of the loudspeaker are convenient, the loudspeaker is installed in the middle section radome fairing, and the sound transmission hole is opened on the middle section radome fairing. The fairing assembly is of an elliptical rotating body structure, and the section of the fairing assembly corresponds to the airfoil curve. The other end of the support rod is of a taper sleeve structure, so that the installation of a calibration sound source in airflow in test occasions such as wind tunnels is realized. The inside of the supporting rod is provided with a wiring channel for arranging a loudspeaker signal wire. The sound transmission channel is used for transmitting sound waves generated by the loudspeaker out of the fairing to form a point sound source; the support rod is used for connecting other equipment to realize the installation of the calibration sound source in wind tunnels and other occasions. The loudspeaker is connected to the support frame through a screw, a high-sound-intensity loudspeaker is adopted, and a sealing ring is adopted at the connecting part for sealing treatment; the sound production part of the loudspeaker is connected with the inlet of the sound transmission channel, and the generated sound waves can enter the sound transmission channel; the sound transmission channel is fixedly connected with the support frame through a screw, and the connecting part is sealed by adopting a sealing ring; the sound-transmitting holes are covered with a layer of Kaffra cloth for separating air flow, so that strong noise interference caused by high-speed air flow rushing into the sound-transmitting channels 5 is avoided, and sound waves generated by a loudspeaker are allowed to be transmitted. This embodiment adopts the good radome fairing of aerodynamic configuration to separate the air current, reduces the aerodynamic force that the calibration sound source received, reduces the interference to the flow field simultaneously, avoids producing extra noise interference, and the sound wave that the speaker produced passes outward along the sound transmission passageway to through the sound transmission hole radiation come out, in order to reduce the sound source area, directive property when guaranteeing its high frequency. The fairing assembly adopts a segmentation and blocking mode, so that the installation, wiring and maintenance of the internal loudspeaker are facilitated.
Claims (6)
1. A sound source calibrating device used in high-speed airflow comprises a fairing assembly, a support frame, a loudspeaker, a sound transmission channel and a support rod, and is characterized in that the fairing assembly is provided with a sound transmission hole, the loudspeaker and the support frame are both arranged in the fairing assembly, the loudspeaker is fixedly connected with the support frame, the sound production part of the loudspeaker is connected with the inlet of the sound transmission channel, the sound transmission channel is fixedly connected with the support frame, the outlet of the sound transmission channel is communicated with the sound transmission hole on the fairing assembly, and one end of the support rod penetrates through the fairing assembly and is fixedly connected with the support frame; the sound transmission holes are covered with a layer of Kaffra cloth.
2. A collimated sound source apparatus for use in high velocity air streams as claimed in claim 1, wherein: the fairing assembly comprises a front fairing, a middle fairing and a rear fairing, wherein the interiors of the front fairing, the middle fairing and the rear fairing are respectively and fixedly connected with the supporting frame.
3. A collimated sound source apparatus for use in high velocity air streams as claimed in claim 2, wherein: the loudspeaker is arranged in the middle section fairing, and the sound transmission hole is formed in the middle section fairing.
4. A collimated sound source apparatus for use in high velocity air streams as claimed in any one of claims 1 to 3, wherein: the fairing assembly is of an elliptical rotating body structure, and the section of the fairing assembly corresponds to the airfoil curve.
5. A collimated sound source apparatus for use in high velocity air streams as claimed in any one of claims 1 to 3, wherein: the other end of the supporting rod is of a taper sleeve structure.
6. A collimated sound source apparatus for use in high velocity air streams as claimed in any one of claims 1 to 3, wherein: the inside of the supporting rod is provided with a wiring channel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911247482.XA CN110793624A (en) | 2019-12-09 | 2019-12-09 | Sound source calibrating device used in high-speed airflow |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911247482.XA CN110793624A (en) | 2019-12-09 | 2019-12-09 | Sound source calibrating device used in high-speed airflow |
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| CN110793624A true CN110793624A (en) | 2020-02-14 |
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| CN201911247482.XA Pending CN110793624A (en) | 2019-12-09 | 2019-12-09 | Sound source calibrating device used in high-speed airflow |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113766389A (en) * | 2021-11-10 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Sound production device and system |
| CN114088197A (en) * | 2021-11-19 | 2022-02-25 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-noise airflow internal noise measuring device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101571448A (en) * | 2009-06-08 | 2009-11-04 | 南京常荣噪声控制环保工程有限公司 | Aero-acoustic experimental apparatus |
| CN104317982A (en) * | 2014-08-26 | 2015-01-28 | 中国直升机设计研究所 | Opening straight-flow wind tunnel low-noise design method |
| WO2019063070A1 (en) * | 2017-09-27 | 2019-04-04 | Harman Becker Automotive Systems Gmbh | Loudspeaker arrangement |
| CN210603585U (en) * | 2019-12-09 | 2020-05-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Sound source calibrating device used in high-speed airflow |
-
2019
- 2019-12-09 CN CN201911247482.XA patent/CN110793624A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101571448A (en) * | 2009-06-08 | 2009-11-04 | 南京常荣噪声控制环保工程有限公司 | Aero-acoustic experimental apparatus |
| CN104317982A (en) * | 2014-08-26 | 2015-01-28 | 中国直升机设计研究所 | Opening straight-flow wind tunnel low-noise design method |
| WO2019063070A1 (en) * | 2017-09-27 | 2019-04-04 | Harman Becker Automotive Systems Gmbh | Loudspeaker arrangement |
| CN210603585U (en) * | 2019-12-09 | 2020-05-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Sound source calibrating device used in high-speed airflow |
Non-Patent Citations (1)
| Title |
|---|
| 谷嘉锦: "高声强声源及其应用", 声学技术, no. 01, 5 February 1997 (1997-02-05) * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113766389A (en) * | 2021-11-10 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Sound production device and system |
| CN114088197A (en) * | 2021-11-19 | 2022-02-25 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-noise airflow internal noise measuring device |
| CN114088197B (en) * | 2021-11-19 | 2023-07-14 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-noise air flow internal noise measuring device |
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